| Doc Number |
Title |
| AD.06.20.09 |
AD 2006-20-09 To Prevent Failure of the Crankshaft (Applicable to Lycoming Engines (L)O-360, (L)IO-360, AEIO-360, O-540, IO-540, AEIO-540, (L)TIO-540, IO-580, and IO-720 Series Reciprocating Engines) |
| AD.06.20.01 |
AD 2006-20-01 To Prevent Pitch Oscillations During Turbulence (Applicable to Airbus Model A310 Airplanes) |
| AD.06.20.02 |
AD 2006-20-02 To Prevent Rapid Decompression of the Airplane Due to Disbonding and Subsequent Cracking of the Skin Panels (Applicable to Boeing Model 747 Airplanes) |
| AD.06.20.03 |
AD 2006-20-03 To Prevent Disengagement of the Telescopic Girt Bar from the Airplane When the Door is Opened in Emergency Situations (Applicable to Airbus Model A319, A320, and A321 Airplanes) |
| AD.06.20.04 |
AD 2006-20-04 To Prevent Breakage Of The Elevator Trim Chain (Applicable to Bombardier Model DHC-8-102, -103, and -106 Airplanes, and Model DHC-8-200 and DHC-8-300 Series Airplanes) |
| AD.06.20.05 |
AD 2006-20-05 To Detect And Correct Such Chafing Or Scoring In This Area (Applicable to BAE Systems (Operations) Limited Model BAe 146 Airplanes) |
| AD.06.19.07 |
AD 2006-19-07 To Prevent Damage to the Airplane and Hazards to Persons or Property on the Ground (Applicable to Airbus Model A330, A340-200, and A340-300 Airplanes) |
| AD.06.19.09 |
AD 2006-19-09 To Prevent the Passenger Seats from Failing During Emergency Landing Conditions (Applicable to Raytheon Aircraft Company Model B300 Airplanes) |
| AD.06.19.02 |
AD 2006-19-02 To Prevent Fatigue Cracking Of The Outer Skin Of The Fuselage At Certain Frames (Applicable to Airbus Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and Model A300 C4-605R Variant F Airplanes (Collectively Called A300-600 Series Airplanes)) |
| AD.06.19.03 |
AD 2006-19-03 To Prevent Damage To The Wire Support Bracket And Wiring Of The Auxiliary Hydraulic Pump (Applicable to McDonnell Douglas Model DC-10-10 and DC-10-10F Airplanes; Model DC-10-15 Airplanes; Model DC-10-30 and DC-10-30F (KC-10A and KDC-10) Airplanes; Model DC-10-40 and DC-10-40F Airplanes; Model MD-10-10F and MD-10-30F Airplanes; and Model MD-11 and MD-11F Airplanes) |
| AD.06.19.05 |
AD 2006-19-05 To Prevent Failure Of The T/R Slider (Applicable to Certain Restricted Category Type-certificated Helicopters) |
| AD.06.18.12 |
AD 2006-18-12 To Prevent False Warning Indications To The Flightcrew From The Hot Detection System Of The Tail Pipe Harness Of The Engine Nacelles (Applicable to Saab Model SAAB-Fairchild SF340A (SAAB/SF340A) and SAAB 340B Airplanes) |
| AD.06.18.13 |
AD 2006-18-13 To Prevent The Loss Of The Hardover Prevention System (HOPS) In The Roll Axis Due To A Short Circuit In The Wiring Harness (Applicable to Gulfstream Model GV and GV-SP Series Airplanes) |
| AD.06.18.14 |
AD 2006-18-14 To Prevent Cracks Leading To Turbine Disc Failure (Applicable to Rolls-Royce Deutschland Ltd & Co KG Tay 650-15 and Tay 651-54 Turbofan Engines) |
| AD.06.18.16 |
AD 2006-18-16 To Detect Spigot Bearings That Are Not Positioned Flush With The Fitting Assembly (Applicable to Raytheon Aircraft Company Model 390 Airplanes) |
| AD.06.18.05 |
AD 2006-18-05 To Prevent Contamination Of Certain Electrical Connectors (Applicable to McDonnell Douglas Model DC-9-14, DC-9-15, and DC-9-15F Airplanes; Model DC-9-21 Airplanes; Model DC-9-30 Series Airplanes; Model DC-9-41 Airplanes; and Model DC-9-51 Airplanes) |
| AD.06.18.06 |
AD 2006-18-06 To Detect And Correct Reduced Structural Integrity Of The Engine Pylon (Applicable to Airbus Model A318, A319, A320, and A321 Airplanes) |
| AD.06.18.07 |
AD 2006-18-07 To Prevent the Loss of Voice Communication (Applicable to Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model ERJ 170 Airplanes) |
| AD.06.17.07 |
AD 2006-17-07 To Prevent A Rupture Of An HPC Front Hub Or An HPC Disk (Applicable to Pratt & Whitney JT8D-1, -1A, -1B, -7, -7A, -7B, -9, -9A, -11, -15, -15A, -17, -17A, -17R, -17AR, -209, -217, -217A, -217C, and -219 Turbofan Engines) |
| AD.06.18.02 |
AD 2006-18-02 To Ensure that the Fuel Vent Lines are Properly Bonded to the Airplane Structure (Applicable to McDonnell Douglas Model DC-9-10, -20, -30, -40, and -50 Series Airplanes) |
| AD.06.17.15 |
AD 2006-17-15 To Ensure That The Fuel Vent Pipes Are Properly Bonded To The Airplane Structure (Applicable to McDonnell Douglas Model DC-10-10 and DC-10-10F Airplanes; and Model MD-10-10F Airplanes) |
| AD.06.17.16 |
AD 2006-17-16 To Detect and Correct Corrosion of the Wing Rear Spar Lower Girder (Applicable to Fokker Model F.28 Mark 0070 and 0100 Airplanes) |
| AD.06.17.17 |
AD 2006-17-17 To Prevent Shear Failure Of Rivets In The Control Column Torque Tube (Applicable to Bombardier Model DHC-8-100, DHC-8-200, DHC-8-300, and DHC-8-400 Series Airplanes) |
| AD.06.17.08 |
AD 2006-17-08 To Prevent Uncontained Engine Failure (Applicable to Pratt & Whitney PW4077D, PW4084D, PW4090, and PW4090?3 Turbofan Engines) |
| AD.06.17.10 |
AD 2006-17-10 To Prevent Fumes, Traces Of Visible Smoke, And Fire At The Fluorescent Light Tube Assembly (Applicable to Bombardier Model DHC-8-100, DHC-8-200, and DHC-8-300 Series Airplanes) |
| AD.06.17.11 |
AD 2006-17-11 To Prevent Failure Of The Safety Fittings For The Cargo Fire Extinguishing Bottles Due To Corrosion (Applicable to Boeing Model 767-400ER Series Airplanes and Model 777-200 and -300 Series Airplanes) |
| AD.06.17.12 |
AD 2006-17-12 To Prevent Possible Disc Failure (Applicable to Rolls-Royce plc RB211 Series Turbofan Engines) |
| AD.06.17.13 |
AD 2006-17-13 To Prevent a Seat Belt from Detaching Due to a Loose Locknut and Attachment Bolt (Applicable to RECARO Aircraft Seating GmbH & Co. (RECARO) Model 3410 Seats) |
| AD.06.18.11 |
AD 2006-18-11 To Prevent Structural Overload Of The Auxiliary Fuel Tank Support Structure (Applicable to Boeing Model 737-200, -300, -400, and -500 Series Airplanes Equipped With an Auxiliary Fuel System Installed in Accordance With Supplemental Type Certificate (STC) SA83NE, SA1078NE, SA725NE, ST00040NY, or ST01337NY) |
| AD.06.16.17 |
AD 2006-16-17 To Prevent Improper Torque of Screws (Applicable to Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-135BJ, -135ER, -135KE, -135KL, and -135LR Airplanes; and Model EMB-145, -145ER, -145MR, -145LR, -145XR, -145MP, and -145EP Airplanes) |
| AD.06.16.18 |
AD 2006-16-18 To Prevent A Bearing Error (Applicable to Sandel Avionics Incorporated Model ST3400 Terrain Awareness Warning System/Radio Magnetic Indicator (TAWS/RMI) Units Approved Under Technical Standard Order(s) C113, C151a, or C151b; Installed on Various Small and Transport Category Airplanes) |
| AD.06.16.14 |
AD 2006-16-14 To Prevent Incorrect Alignment of the Actuator and the Drive Assembly (Applicable to Airbus Model 318, A319, A320, and A321 Airplanes) |
| AD.06.16.15 |
AD 2006-16-15 To Prevent The Un-commanded Descent Of An Airplane Below The Selected Level-off Altitude (Applicable to McDonnell Douglas Model MD-10-10F and MD-10-30F Airplanes and Model MD-11 and MD-11F Airplanes) |
| AD.06.16.16 |
AD 2006-16-16 To Detect And Correct Such Discrepancies On The Forward Baggage Compartment Partition (Applicable to Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-135BJ Airplanes) |
| AD.06.17.01 |
AD 2006-17-01 To Detect and Correct Torque Transducers that are out of Calibration (Applicable to Mitsubishi Heavy Industries MU-2B Series Airplanes) |
| AD.06.17.02 |
AD 2006-17-02 To Prevent Cracks in the Spherical Locking Bolt (Applicable to GROB-WERKE GMBH & CO KG Model G102 ASTIR CS Sailplanes) |
| AD.06.17.03 |
AD 2006-17-03 To Prevent a Loose Bearing in the Aileron Control Lever (Applicable to Stemme GmbH & Co. KG Models S10, S10-V, and S10-VT Sailplanes) |
| AD.06.18.09 |
AD 2006-18-09 To Detect and Correct Fatigue Cracking of Certain Structural Elements (Applicable to BAE Systems (Operations) Limited Model ATP Airplanes) |
| AD.06.16.13 |
AD 2006-16-13 To Identify Drill Damage on Some Frame 21 (FR21) Lug Fittings (Applicable to Pilatus Aircraft Ltd. Models PC-12 and PC-12/45 Airplanes) |
| AD.06.16.19 |
AD 2006-16-19 To Prevent Corroded Elevator FInal Drive Control Rods (Applicable to B-N Group Ltd. BN-2, BN-2A, BN-2B, BN-2T, and BN-2T-4R Series (All Individual Models Included in Type Certificate Data Sheet (TCDS) A17EU, Revision 16, Dated December 9, 2002) Airplanes) |
| AD.06.16.20 |
AD 2006-16-20 To Prevent The Rigging Of The Horizontal Stabilizer Without Properly Connecting The Elevator (Applicable to DG Flugzeugbau GmbH Model DG-1000S Sailplanes) |
| AD.06.02.08 |
AD 2006-02-08 R1 To Prevent In-flight Engine Shutdown (Applicable to Turbomeca Arriel 1B, 1D, 1D1, and 1S1 Turboshaft Engines) |
| AD.06.16.09 |
AD 2006-16-09 To Prevent Arcing on the In-Tank Side of the Fueling Valve During a Lightning Strike (Applicable to McDonnell Douglas Model MD-90-30 Airplanes) |
| AD.06.16.10 |
AD 2006-16-10 To Detect and Correct Cracking, Buckling, Wrinkling, or Heat Damage of the Skin and Internal Structure of the Engine Struts (Applicable to Boeing Model 747-200B, 747-200C, 747-200F, 747-300, and 747SR Series Airplanes) |
| AD.06.16.11 |
AD 2006-16-11 To Detect and Correct Fatigue Cracks (Applicable to Boeing Model 737-700 and 737-800 Series Airplanes) |
| AD.06.16.05 |
AD 2006-16-05 To Prevent Front Pylon Mount Bolt and Primary Mount Thrust Load Path Failure (Applicable to Pratt & Whitney PW4164, PW4168, and PW4168A Series Turbofan Engines) |
| AD.06.16.02 |
AD 2006-16-02 To Prevent Arcing on the In-Tank Side of the Fueling Valve During a Lightning Strike (Applicable to McDonnell Douglas Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87), and MD-88 Airplanes) |
| AD.06.16.03 |
AD 2006-16-03 To Reduce the Potential of Ignition Sources Inside Fuel Tanks in the Event of a Severe Lightning Strike (Applicable to McDonnell Douglas Model DC-10-10, DC-10-10F, DC-10-15, DC-10-30, DC-10-30F (KC-10A and KDC-10), DC-10-40, and DC- 10-40F Airplanes) |
| AD.06.16.04 |
AD 2006-16-04 To Minimize The Risk Of Sudden Loss Of Engine Power And Uncommanded Shutdown Of The Engine (Applicable to Rolls-Royce Corporation (Formerly Allison Engine Company, Allison Gas Turbine Division, and Detroit Diesel Allison) (RRC) 250-B and 250-C Series Turboshaft and Turboprop Engines) |
| AD.06.15.15 |
AD 2006-15-15 To Prevent Shorted Wires or Arcing at the Auxiliary Hydraulic Pump (Applicable to McDonnell Douglas Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87), and MD-88 Airplanes) |
| AD.06.15.16 |
AD 2006-15-16 To Prevent Over-voltage Conditions Of The DC Starter Generator (Applicable to Raytheon (Beech) Model 400 and 400A Series Airplanes) |
| AD.06.15.17 |
AD 2006-15-17 To Prevent Failure Of The Sliding Window Heating Element(s) (Applicable to Fokker Model F.28 Mark 0070 and 0100 Airplanes) |
| AD.06.15.18 |
AD 2006-15-18 To Prevent A Single Fault Failure In Flight From Simulating A Test Condition And Showing Test Patterns Instead Of The Selected Radio Frequencies (Applicable to Boeing Model 737-300, -400, -500, -600, -700, -700C, -800, and -900 Series Airplanes) |
| AD.06.16.06 |
AD 2006-16-06 To Detect And Prevent Cracks In The Bottoms Of The Dovetail Slots (Applicable to General Electric Company (GE) CF6-80 Series Turbofan Engines) |
| AD.06.17.04 |
AD 2006-17-04 To Detect and Correct any Incorrect Torque Values of the End Fittings of Flexible Fuel Hoses in the Engine Compartment (Applicable to The Cessna Aircraft Company Models 172R, 172S, 182T, T182T, 206H, and T206H Airplanes) |
| AD.06.15.14 |
AD 2006-15-14 To Prevent Fatigue Failure Of A Fixed Bolt And Main Rotor Nut (Applicable to Eurocopter Canada Limited Model BO 105 LS A-3 Helicopters) |
| AD.04.16.15 |
AD 2004-16-15 R1 To Detect A Crack In The MGB Base Plate (Applicable to Eurocopter France Model AS-365N2, AS 365 N3, EC 155B, EC155B1, SA-365N, N1, and SA-366G1 Helicopters) |
| AD.06.15.09 |
AD 2006-15-09 To Ensure Continuous Electrical Bonding Protection of Equipment in the Wing (Applicable to Airbus Model A300 Airplanes; Model A310 Airplanes; and Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and Model C4-605R Variant F Airplanes (Collectively Called A300-600 Series Airplanes) |
| AD.06.15.10 |
AD 2006-15-10 To Prevent a Possible Failure of High-Time Units (Applicable to Airbus Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and Model C4-605R Variant F Airplanes (Collectively Called A300-600 Series Airplanes); and Airbus Model A310-200 and -300 Series Airplanes) |
| AD.06.15.11 |
AD 2006-15-11 To Prevent a Hazardous Quantity of Smoke, Flames, and/or Fire Extinguishing Agent from the Cargo Compartment from Entering a Compartment Occupied by Passengers or Crew (Applicable to Construcciones Aeronauticas, S.A. (CASA), Model C-212-CC Airplanes) |
| AD.06.15.04 |
AD 2006-15-04 To Detect And Correct Fatigue Cracks In The Lower Flanges Of The Left And Right Gantries 1 Through 5 (Applicable to Airbus Model A300 B2 and B4 Series Airplanes; and Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and Model C4-605R Variant F Airplanes (Collectively Called A300-600 Series Airplanes)) |
| AD.06.15.05 |
AD 2006-15-05 To Prevent Contamination Of The Fueling Float Switch Of The Auxiliary Fuel Tank By Moisture Or Fuel (Applicable to Boeing Model 737-200, -300, and -400 Series Airplanes) |
| AD.06.15.06 |
AD 2006-15-06 To Prevent A Sudden Change In Pitch Due To An Out-of-trim Condition Combined With An Autopilot Disconnect (Applicable to Airbus Model A300 B2-203 and A300 B4-203 Airplanes; Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and Model C4-605R Variant F Airplanes (Collectively Called A300-600 Series Airplanes); and Model A310-200 and -300 Series Airplanes) |
| AD.06.15.07 |
AD 2006-15-07 To Detect And Correct Improper Rigging Of The Propeller Feathering Linkage (Applicable to Mitsubishi Heavy Industries, Ltd. MU-2B Series Airplanes) |
| AD.06.15.02 |
AD 2006-15-02 To Detect and Correct Increased Friction in the Aileron Control Bellcrank Assemblies (Applicable to Pilatus Aircraft Ltd. Models PC-6, PC-6-H1, PC-6-H2, PC-6/350, PC-6/350-H1, PC-6/350-H2, PC-6/A, PC-6/A-H1, P--6/A-H2, PC-6/B-H2, PC-6/B1-H2, PC-6/B2-H2, PC-6/B2-H4, PC-6/C-H2, and PC-6/C1-H2 Airplanes) |
| AD.06.15.03 |
AD 2006-15-03 To Detect And Correct Cracks In The Ribs Of The Inboard Integral Fuel Tanks (Applicable to Pilatus Aircraft Ltd. Models PC-6, PC-6-H1, PC-6-H2, PC-6/350, PC-6/350-H1, PC-6/350-H2, PC-6/A, PC-6/A-H1, PC-6/A-H2, PC-6/B-H2, PC-6/B1-H2, PC-6/B2-H2, PC-6/B2-H4, PC-6/C-H2, and PC-6/C1-H2 Airplanes) |
| AD.06.14.07 |
AD 2006-14-07 To Detect and Correct Cracking, Corrosion, Interlaminar Corrosion, Delamination, and Disbonding in the Elevator Rear Spar (Applicable to Boeing Model 737-100, -200, and -200C Series Airplanes) |
| AD.06.14.08 |
AD 2006-14-08 To Prevent Incorrect Flight Idle Blade Angle Settings (Applicable to Mitsubishi Heavy Industries MU-2B Series Airplanes) |
| AD.06.14.09 |
AD 2006-14-09 To Prevent a Decrease in the Torque Limiter Function (Applicable to Airbus Model A330-200 and -300, and A340-200 and -300 Series Airplanes) |
| AD.06.14.05 |
AD 2006-14-05 To Prevent Failure of the Lower Panel of the MLG Door (Applicable to Bombardier Model CL-600-2C10 (Regional Jet Series 700, 701, and 702) Airplanes, Model CL-600-2D15 (Regional Jet Series 705) Airplanes, and Model CL-600-2D24 (Regional Jet Series 900) Airplanes) |
| AD.06.13.15 |
AD 2006-13-15 To Detect And Correct Cracks, Corrosion, Fractures, And Incorrect Torque Values (Applicable to Mitsubishi Heavy Industries MU-2B Series Airplanes) |
| AD.06.13.18 |
AD 2006-13-18 To Prevent Point-contact Arcing Or Filament Heating In The Fuel Tank (Applicable to McDonnell Douglas Model DC-9-31, DC-9-32, DC-9-32F, DC-9-33F, DC-9-34, and DC-9-34F Airplanes; and Model DC-9-40 and DC-9-50 Series Airplanes) |
| AD.06.14.01 |
AD 2006-14-01 To Detect And Correct Improper Routing Of The Electrical Harnesses Of Certain Slide/Rafts (Applicable to Airbus Model A330-200, A330-300, A340-200, and A340-300 Series Airplanes, and Model A340-541 and A340-642 Airplanes) |
| AD.06.14.02 |
AD 2006-14-02 To Prevent Failure Of The Landing Gear Lengthening System (Applicable to Airbus Model A330-200 and A330-300 Series Airplanes, and Airbus Model A340-200 and A340-300 Series Airplanes) |
| AD.06.14.03 |
AD 2006-14-03 To Prevent Uncontained Failure Of The Turbine Rotor Due To Low-cycle-fatigue (LCF) (Applicable to Honeywell International Inc. TPE331 Series Turboprop, and TSE331-3U Model Turboshaft Engines) |
| AD.06.13.10 |
AD 2006-13-10 To Prevent Water Accumulation in the Rudder Trim Tab (Applicable to Raytheon Aircraft Company 65, 90, 99, and 100 Series Airplanes) |
| AD.06.13.11 |
AD 2006-13-11 To Correct Improper Aileron Assembly Configuration (Applicable to Pilatus Aircraft Ltd. Models PC-6, PC-6-H1, PC-6-H2, PC-6/350, PC-6/350-H1, PC-6/350-H2, PC-6/A, PC-6/A-H1, PC-6/A-H2, PC-6/B-H2, PC-6/B1-H2, PC-6/B2-H2, PC-6/B2-H4, PC-6/C-H2, and PC-6/C1-H2 Airplanes) |
| AD.06.10.19 |
AD 2006-10-19 To Detect Jamming Of The Twist Grip Assembly (Applicable to Eurocopter France Model EC130 B4 Helicopters) |
| AD.06.13.07 |
AD 2006-13-07 To Prevent A Possible Flammable Condition (Applicable to McDonnell Douglas Model MD-11 and MD-11F Airplanes) |
| AD.06.13.08 |
AD 2006-13-08 To Prevent Anti-fretting Material Contamination (Applicable to Airbus Model A330-200, A330-300, A340-200, and A340-300 Series Airplanes; and Model A340-541 and A340-642 Airplanes) |
| AD.06.13.04 |
AD 2006-13-04 To Prevent Cracking in the Web of Nose Rib 7 (Applicable to Airbus Model A300 B2 and A300 B4 Series Airplanes; and Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and Model C4-605R Variant F Airplanes (Collectively Called A300-600 Series Airplanes) |
| AD.06.13.01 |
AD 2006-13-01 To Detect And Correct Cracking Of The Forward Frame And Fuselage Skin Of The No. 3 Cargo Door Cutout (Applicable to Boeing Model 727-200 Series Airplanes Equipped With a No. 3 Cargo Door) |
| AD.06.13.02 |
AD 2006-13-02 To Prevent Incorrect Operation of the Negative Pressure Relief Valve (Applicable to Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model ERJ 170 Airplanes) |
| AD.06.12.18 |
AD 2006-12-18 To Prevent Ignition Sources Inside the Fuel Tanks (Applicable to Short Brothers Model SD3 Airplanes) |
| AD.06.12.21 |
AD 2006-12-21 To Prevent An Unannunciated Failure Of The Flap System (Applicable to Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) Airplanes) |
| AD.06.12.22 |
AD 2006-12-22 To Detect and Correct Cracks and/or Marks on the RAT Carbon Blades (Applicable to Airbus Model A319, A320, and A321 Airplanes) |
| AD.06.12.24 |
AD 2006-12-24 To Prevent Failure Of The Side Links And Possible Engine Separation From The Airplane (Applicable to General Electric Company CF6 Series Turbofan Engines) |
| AD.06.12.13 |
AD 2006-12-13 To Prevent Fatigue Cracking Of The Main Landing Gear (MLG) Attachment Fittings (Applicable to Airbus Model A300 B2 and A300 B4 Series Airplanes; A300 B4-600, B4-600R, and F4-600R Series Airplanes; and Model C4-605R Variant F Airplanes (Collectively Called A300-600 Series Airplanes)) |
| AD.06.12.14 |
AD 2006-12-14 To Prevent A Potential Source Of Ignition Near A Fuel Tank (Applicable to Empresa Brasileira del Aeronautica S.A. (EMBRAER) Model EMB-120, -120ER, -120FC, -120QC, and -120RT Airplanes) |
| AD.06.12.15 |
AD 2006-12-15 To Detect And Correct Cracked Fuel Access Panels (Applicable to Bombardier Model DHC-8-400 Series Airplanes) |
| AD.06.12.16 |
AD 2006-12-16 To Prevent Failure Of A Door Attachment (Applicable to Bombardier Model DHC-8-102, -103, -106, -201, -202, -301, -311, -314, and -315 Airplanes; Equipped With Certain Cockpit Door Installations) |
| AD.06.12.17 |
AD 2006-12-17 To Detect And Correct Cracking Of The Fuselage Frames From BS 360 To BS 500B (Applicable to Boeing Model 737-200C Series Airplanes) |
| AD.06.12.01 |
AD 2006-12-01 To Prevent, In The Event Of A Lightning Strike To The Horizontal Stabilizer, Sparking Of Metal Parts And Debris (Applicable to Airbus Model A300 B4-600R Series Airplanes, A300 C4-605R Variant F Airplanes, A300 F4-600R Series Airplanes; and Model A310-300 Series Airplanes) |
| AD.06.12.08 |
AD 2006-12-08 To Prevent Loss of Pressure in the Escape Slides/Rafts after an Emergency Evacuation (Applicable to Goodrich Evacuation Systems Approved Under Technical Standard Order (TSO) TSOC69b and Installed on Airbus Model A330-200 and -300 Series Airplanes, Model A340-200 and -300 Series Airplanes, and Model A340-541 and -642 Airplanes) (See Correcting Fed. Reg. 71 FR 36674, June 28, 2006) |
| AD.06.12.09 |
AD 2006-12-09 To Prevent Reduced Structural Integrity of the Airplane (Applicable to BAE Systems (Operations) Limited Model BAe 146 and Avro 146-RJ Airplanes) |
| AD.06.12.10 |
AD 2006-12-10 To Prevent Failure of the Oxygen Cylinder Support Under the Most Critical Flight Load Conditions (Applicable to Boeing Model 747-400 Series Airplanes) |
| AD.06.12.11 |
AD 2006-12-11 To Prevent Exposed Wires That Could Provide An Ignition Source (Applicable to Boeing Model 737-600, -700, -700C, -800, and -900 Series Airplanes) |
| AD.06.11.18 |
AD 2006-11-18 To Detect and Correct Damaged Wires on the Left-Hand (LH) and Right-Hand (RH) Sides of the Forward End of the Cockpit Center Console (Applicable to Pacific Aerospace Corporation Ltd. Model 750XL Airplanes) |
| AD.06.12.05 |
AD 2006-12-05 To Detect And Correct Damage Of The Center Tank Fuel Pumps And Fuel Pump Canisters (Applicable to Airbus Model A300 B4 Series Airplanes; Model A300 B4-600 Series Airplanes; Model A300 C4-605R Variant F Airplanes; Model A310-200 Series Airplanes; and Model A310-300 Series Airplanes) |
| AD.06.12.07 |
AD 2006-12-07 To Prevent Loss Of Engine Power Due To Cracks In The Cylinder Assemblies (Applicable to Engine Components Inc. (ECi) Reciprocating Engine Cylinder Assemblies) |
| AD.06.11.17 |
AD 2006-11-17 To Prevent Restricting full Lateral Movement of the Cyclic Control (Applicable to Eurocopter France Model AS350B, BA, B1, B2, B3, C, D, and D1 Helicopters) |
| AD.06.10.18 |
AD 2006-10-18 To Ensure That The Flightcrew Is Provided With Correct Information To Ensure A Safe Takeoff (Applicable to Gulfstream Aerospace LP Model Galaxy and Model Gulfstream 200 Airplanes) |
| AD.06.12.02 |
AD 2006-12-02 To Prevent the Presence of a Combustible Air-Fuel Mixture in the Fuel Tank Boost Pump (Applicable to Airbus Model A318, A319, A320, and A321 Airplanes) |
| AD.06.12.20 |
AD 2006-12-20 To Prevent Loss of all Primary Electrical Power (Applicable to Raytheon Model HS.125 Series 700A and 700B Airplanes; Model BAe.125 Series 800A Including Variants C-29A and U-125), 800B, 1000A, and 1000B Airplanes; and Hawker 800 (Including Variant U-125A), 800XP, and 1000 Airplanes) |
| AD.06.11.09 |
AD 2006-11-09 To Detect and Correct Cracking in the Lower Forward Corner of the Cargo Door Skin Cut-Out (Applicable to Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) Airplanes) |
| AD.06.11.10 |
AD 2006-11-10 To Prevent a Potential Source of Ignition Near a Fuel Tank (Applicable to Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-120, -120ER, -120FC, -120QC, and -120RT Airplanes) |
| AD.06.11.11 |
AD 2006-11-11 To Ensure That Fatigue Cracking Of Various PSEs Is Detected And Corrected (Applicable to Boeing Model 757 Airplanes) |
| AD.06.11.12 |
AD 2006-11-12 To Prevent Excessive Vibration of the Airframe During Flight (Applicable to Boeing Model 767 Airplanes) |
| AD.06.11.03 |
AD 2006-11-03 To Prevent Broken Damper Shafts (Applicable to Gulfstream Model GV and GV-SP Series Airplanes) |
| AD.06.11.06 |
AD 2006-11-06 To Prevent The Stowage Bins From Opening During Flight Turbulence Or A Hard Landing (Applicable to Boeing Model 767-200 and -300 Series Airplanes) |
| AD.06.11.07 |
AD 2006-11-07 To Prevent Insufficient Electrical Isolation For The Electrical Bus Configuration (Applicable to Raytheon Model Hawker 800XP Airplanes) |
| AD.06.11.01 |
AD 2006-11-01 To Prevent Damage To The Fuel Pump And Fuel Pump Canister (Applicable to Airbus Model A300 B4-600R and A300 F4-600R Series Airplanes) |
| AD.06.11.02 |
AD 2006-11-02 To Prevent Structural Failure Of The Airplane Due To Corrosion (Applicable to Viking Air Limited Model DHC-7 Airplanes) |
| AD.06.04.11 |
AD 2006-04-11 R1 To Detect And Correct Fatigue Cracking On The Inner Rear Spar Of The Wings (Applicable to Airbus Model A321-100 Series Airplanes) |
| AD.06.10.17 |
AD 2006-10-17 To Prevent Wire Bundles From Contacting The Overhead Dripshield Panel (Applicable to Boeing Model 737-600, -700, -700C, -800, and -900 Series Airplanes) |
| AD.06.10.21 |
AD 2006-10-21 To Prevent Fatigue Failure Of The Connecting Rod (Applicable to Engine Components Incorporated (ECi) Reciprocating Engine Connecting Rods) (See Correcting Federal Register 71 FR 34811, June 16, 2006) |
| AD.06.10.12 |
AD 2006-10-12 To Prevent Corrosion Of Flight Control Surface Bearings And Freezing Of Moisture Inside The Bearings (Applicable to AE Systems (Operations) Limited Model BAe 146 Airplanes and Model Avro 146-RJ Airplanes) |
| AD.06.10.14 |
AD 2006-10-14 To Prevent Cracks In The Cargo Door Pan (Applicable to McDonnell Douglas Model DC-9-10, DC-9-20, DC-9-30, DC-9-40, and DC-9-50 Series Airplanes; Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), and DC-9-87 (MD-87) Airplanes; Model MD-88 Airplanes; Model MD-90-30 Airplanes; and Model 717-200 Airplanes) |
| AD.06.10.16 |
AD 2006-10-16 To Detect And Correct Cracking In The Outboard And Center Section Of The Aft Upper Skin Of The Horizontal Stabilizer (Applicable to Boeing Model 747 Airplanes) |
| AD.06.10.09 |
AD 2006-10-09 To Prevent a Potential Source of Ignition Near a Fuel Tank (Applicable to Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-120, -120ER, -120FC, -120QC, and -120RT Airplanes in Operation) |
| AD.06.10.10 |
AD 2006-10-10 To Prevent Loose Electrical Connections that Could arc and Overheat (Applicable to Bombardier Model BD-100-1A10 Airplanes) |
| AD.06.10.11 |
AD 2006-10-11 To Detect And Correct Cracking Of The Flap Transmission Shaft (Applicable to Airbus Model A310-200 and -300 Series Airplanes) |
| AD.06.09.11 |
AD 2006-09-11 To Detect And Correct Corrosion And Damage On The Lower Part Of The Lavatory Walls (Applicable to Airbus Model A319-100, A320-200, A321-100, and A321-200 Series Airplanes) |
| AD.06.10.04 |
AD 2006-10-04 To Detect And Correct Cracking In The Longeron Extension Fitting (Applicable to Boeing Model 747-200B, 747-200C, 747-200F, 747-300, 747-400, and 747SP Series Airplanes) |
| AD.06.10.05 |
AD 2006-10-05 To Prevent Failure Of The Uplock Mechanism, Which, Combined With A Loss Of Hydraulic Pressure, Could Result In An Uncommanded Extension Of The MLG (Applicable to Saab Model SAAB-Fairchild SF340A (SAAB/SF340A) and SAAB 340B Airplanes) |
| AD.05.25.05 |
AD 2005-25-05 To Prevent Critical Life-limited Rotating Engine Part Failure (Applicable to Pratt & Whitney JT8D Series Turbofan Engines) |
| AD.05.25.09 |
AD 2005-25-09 To Prevent Critical Life-limited Rotating Engine Part Failure (Applicable to Pratt & Whitney PW4000 Series Turbofan Engines) |
| AD.06.10.01 |
AD 2006-10-01 To Prevent Fluid Contamination Inside the Fire and Overheat Control Unit in the Flight Compartment (Applicable to Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) Airplanes) (See Correcting Federal Register 71 FR 33614, June 12, 2006) |
| AD.06.10.02 |
AD 2006-10-02 To Prevent An Undetected Failure Of The Primary Load Path For The Ballscrew In The Horizontal Stabilizer (Applicable to Boeing Model 747 Airplanes) |
| AD.06.09.04 |
AD 2006-09-04 To Detect and Correct Missing Rivets in the Front Section of the Central Engine Mast (Applicable to Dassault Model Falcon 900EX Airplanes) |
| AD.06.09.05 |
AD 2006-09-05 To Detect And Correct Fatigue Cracks Of The Rear Spar Internal Angle And Tee Fitting (Applicable to Airbus Model A310-200 and -300 Series Airplanes) |
| AD.06.09.06 |
AD 2006-09-06 To Detect And Correct Fatigue Cracking Of Certain Lower Lobe Fuselage Frames (Applicable to Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-300, 747-400, 747-400D, and 747SR Series Airplanes) |
| AD.06.09.07 |
AD 2006-09-07 To Prevent Fatigue Cracking, Damage, or Corrosion (Applicable to Airbus Model A330-200, A330-300, A340-200, and A340-300 Series Airplanes; and A340-541 and A340-642 Airplanes) |
| AD.06.09.09 |
AD 2006-09-09 To Detect and Correct Cracking in the Skin, the Bulkhead Outer Chord (Applicable to Boeing Model 767 Airplanes) |
| AD.06.09.03 |
AD 2006-09-03 To Find and Fix Fatigue Cracking of the Fuselage (Applicable to Boeing Model 727, 727C, 727-100, and 727-100C Series Airplanes) |
| AD.06.08.03 |
AD 2006-08-03 To Prevent Injury Resulting From Contact With The Bottom Folding Mechanism (Applicable to Sicma Aero Seat (Formerly Farner); Cabin Attendant Seats Series 150 Type FN and Series 151 Type WN) |
| AD.06.08.04 |
AD 2006-08-04 To Prevent an Ignition Source from Entering the Fuel Tank During a Lightning Strike Event (Applicable to Boeing Model 767 Airplanes) |
| AD.06.07.21 |
AD 2006-07-21 To Detect And Correct Cracking In The Midspar Fittings Of The Nacelle Struts (Applicable to Boeing Model 757 Airplanes Powered by Pratt & Whitney Engines) |
| AD.06.07.22 |
AD 2006-07-22 To Prevent Deformation of the Cable Duct Structure in the Event of a Rapid Decompression (Applicable to BAE Systems (Operations) Limited Model BAe 146 and Model Avro 146-RJ Airplanes) |
| AD.06.07.23 |
AD 2006-07-23 To Prevent Excessive Vibration Of The Airframe During Flight (Applicable to Boeing Model 757 Airplanes) |
| AD.06.07.24 |
AD 2006-07-24 To Prevent Intermittent Indications In The Flight Deck (Applicable To Boeing Model 757-200 and -300 Series Airplanes) |
| AD.06.07.25 |
AD 2006-07-25 To Prevent Failure Of The Rudder Pedal Bracket Assembly (Applicable to McDonnell Douglas Airplanes) |
| AD.06.07.14 |
AD 2006-07-14 To Prevent Fracture Of The MLG Bogie Beam Pivot Pin (Applicable to Boeing Model 767-200, -300, and -300F Series Airplanes) |
| AD.06.07.16 |
AD 2006-07-16 To Prevent Corrosion Or Perforation Of Domed Anchor Nuts (Applicable to Bombardier Model DHC-8-400 Series Airplanes) |
| AD.06.07.17 |
AD 2006-07-17 To Detect And Correct Stress-corrosion Cracking Of The Terminal Fittings (Applicable to Boeing Model 727, 727C, 727-100, 727-100C, and 727-200 Series Airplanes) |
| AD.06.07.18 |
AD 2006-07-18 To Detect And Correct Corrosion In The Torque Tubes Of The Elevators (Applicable to Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-120, -120ER, -120FC, -120QC, and -120RT Airplanes) |
| AD.06.07.06 |
AD 2006-07-06 To Detect, Correct, And Prevent Damage To The Fuel Line And Wire Bundles (Applicable to Cirrus Design Corporation Models SR20 and SR22 Airplanes) |
| AD.06.07.10 |
AD 2006-07-10 To Prevent the Loss of the Structural Integrity of the Forward Entry Doorway (Applicable to Boeing Model 727 Airplanes) |
| AD.06.07.08 |
AD 2006-07-08 To Detect And Correct Stress Corrosion Cracking Of The Main Fuselage Frame (Applicable to McDonnell Douglas Model DC-9-10, DC-9-20, DC-9-30, DC-9-40, and DC-9-50 Series Airplanes) |
| AD.06.07.09 |
AD 2006-07-09 To Ensure The Integrity Of The THSA's Primary Load Path (Applicable to Airbus Model A318-100 and A319-100 Series Airplanes; Model A320-111 Airplanes; and Model A320-200, A321-100, and A321-200 Series Airplanes) |
| AD.06.07.11 |
AD 2006-07-11 To Prevent Fatigue Cracking of the Aft Attach Fitting of the Spoiler Link (Applicable to McDonnell Douglas Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87), MD-88, and MD-90-30 Airplanes) |
| AD.06.07.12 |
AD 2006-07-12 To Prevent Rapid Decompression Of The Airplane Due To Fatigue Cracks (Applicable to Boeing Model 737-100, -200, -200C, -300, -400, and -500 Series Airplanes) |
| AD.06.07.02 |
AD 2006-07-02 To Ensure That The Pressure Control Valve Does Not Freeze (Applicable to Bombardier Model DHC-8-301, -311, and -315 Airplanes) |
| AD.06.07.03 |
AD 2006-07-03 To Prevent A Punctured Fuel Tank (Applicable to Airbus Model A321-100 and -200 Series Airplanes) |
| AD.06.07.04 |
AD 2006-07-04 To Prevent Drain Blockage By Debris (Applicable to Boeing Model 737-600, -700, -700C, -800, and -900 Series Airplanes) |
| AD.06.06.51 |
AD 2006-06-51 To Prevent Failures of the No. 3 Bearings and Possible Dual In-Flight Shutdowns of the Engines (Applicable to General Electric Company Aircraft Engines (GEAE) CT7-8A Turboshaft Engines) |
| AD.06.06.12 |
AD 2006-06-12 To Prevent Cracking of the Upper Arms of the Secondary Side Brace Assemblies of the MLG (Applicable to Aerospatiale Model ATR72 Airplanes) |
| AD.06.06.13 |
AD 2006-06-13 To Prevent Rupture Of The Inboard And Outboard Actuator Fittings Of The Aileron Servo Controls (Applicable to Airbus Model A330-200 and -300 Series Airplanes; and Model A340-200 and -300 Series Airplanes) (See Correcting Federal Register 71 FR 50506, August 25, 2006) |
| AD.06.06.14 |
AD 2006-06-14 To Prevent an Ignition Source in the Wing Fuel Tank in the Event of a Lightning Strike (Applicable to Airbus Model A318-100 and A319-100 Series Airplanes, A320-111 Airplanes, A320-200 Series Airplanes, and A321-100 and A321-200 Series Airplanes) |
| AD.06.06.15 |
AD 2006-06-15 To Prevent Air Leakage Through The Water Drain Valves (Applicable to Airbus Model A318-100 Series Airplanes; Model A319-100 Series Airplanes; Model A320-111 Airplanes; Model A320-200 Series Airplanes; Model A321-100 Series Airplanes; and Model A321-200 Series Airplanes) |
| AD.06.08.05 |
AD 2006-08-05 To Prevent Reduced Structural Integrity Of The Airplane (Applicable to Fokker Model F.28 Mark 0100 Airplanes) |
| AD.06.06.16 |
AD 2006-06-16 To Prevent Failure of the Crankshaft (Applicable to Lycoming Engines (Formerly Textron Lycoming) AEIO-360, AEIO-360, IO-360, LIO-360, and LO-360 Series Reciprocating Engines) |
| AD.06.06.17 |
AD 2006-06-17 To Detect and Prevent Perforation of the 2nd Stage Nozzle Guide Vanes (NGV2) (Applicable to Turbomeca Arriel 1B, 1D, and 1D1 Turboshaft Engines) |
| AD.06.06.07 |
AD 2006-06-07 To Detect and Correct Cracks in the MLG Main Fitting (Applicable to Fokker Model F.28 Mark 0070 and 0100 Airplanes) |
| AD.06.06.09 |
AD 2006-06-09 To Prevent Failure of the Aileron and Flap/Slat Controls System (Applicable to Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model ERJ 170 Airplanes) |
| AD.06.06.10 |
AD 2006-06-10 To Detect and Correct Cracks in the Skin, Bearstrap, and Small Steel Doubler (Applicable to Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-300, 747-400, 747-400D, and 747SR Series Airplanes) |
| AD.06.06.11 |
AD 2006-06-11 To Detect And Correct Cracking Of The Tension Ties, Shear Webs, And Frames Of The Upper Deck (Applicable to Boeing Model 747-100B SUD, 747-200B, 747-300, 747-400, and 747-400D Series Airplanes) |
| AD.02.11.05 |
AD 2002-11-05 R1 To Prevent Fatigue Cracks from Occurring in the Wing Lower Spar Cap (Applicable to Air Tractor, Inc. Model AT-501 Airplanes) (See Correcting Federal Register 71 FR 27321, May 10, 2006) |
| AD.06.08.08 |
AD 2006-08-08 To Detect and Correct Cracks in the Wing Main Spar Lower Cap (Applicable to Air Tractor, Inc. Models AT-400; AT-401, AT-401B, AT-402, AT-402A, and AT-402B Airplanes) (See correcting Federal Register 71 FR 27794, May 12, 2006) |
| AD.06.06.03 |
AD 2006-06-03 To Prevent Potential Fuel Vapor Ignition In A Fuel Tank (Applicable to Cessna Model 500, 501, 550, S550, 551, and 560 Airplanes) |
| AD.06.06.01 |
AD 2006-06-01 To Prevent Interference of the Wiring with the Structure Resulting in an Electrical Short Circuit (Applicable to Eurocopter France Model EC 155B and B1 Helicopters) |
| AD.05.05.20 |
AD 2005-05-20 To Prevent Failure Of Flight Deck Door Electronic Equipment (Applicable to Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200F, 747-300, 747-400, 747-400D, 747SP, 747SR, 767-200, 767-300, 777-200, 777-300, and 777-300ER Series Airplanes) |
| AD.06.06.02 |
AD 2006-06-02 To Prevent Failure of the Diagonal Cross-Member, Pivoting of the MGP (Applicable to Eurocopter France Model SA-365N, SA-365N1, AS-365N2, and SA-366G1 Helicopters) |
| AD.06.05.06 |
AD 2006-05-06 To Prevent Fatigue Cracking Of The Body Station (BS) 2598 Bulkhead Structure (Applicable to Boeing Model 747 Airplanes) |
| AD.06.05.07 |
AD 2006-05-07 To Prevent Cracking of the Upper Arms of the Side Braces of the MLG (Applicable to Aerospatiale Model ATR42-200, -300, and -320 Airplanes) |
| AD.06.05.08 |
AD 2006-05-08 To Prevent Energy From A Lightning Strike On The Bushing For The Sump Drain Valve From Arcing (Applicable to Boeing Model 777-200 Series Airplanes) |
| AD.06.05.09 |
AD 2006-05-09 To Detect and Correct Fatigue Cracks in the Overlapping (Upper) Skin (Applicable to Boeing Model 747-200C, -200F, -400, -400D, and -400F Series Airplanes) |
| AD.06.03.15 |
AD 2006-03-15 To Prevent Improper Deployment of the Escape Slide/Raft or Blockage of the Passenger/Crew Doors (Applicable to Boeing Model 747SP, 747SR, 747-100, -100B, -100B SUD, -200B, -200C, -200F, and -300 Series Airplanes) |
| AD.06.04.14 |
AD 2006-04-14 To Detect And Correct Loosened End Caps (Applicable to Boeing Model 757-200 and -300 Series Airplanes) |
| AD.06.04.12 |
AD 2006-04-12 To Prevent Low-Cycle-Fatigue (LCF) Failure of Stage 5 LPT Disks and Stage 6 LPT Disks (Applicable to General Electric Company CF34-1A, -3A, -3A1, -3A2, -3B, and -3B1 Series Turbofan Engines) |
| AD.06.05.03 |
AD 2006-05-03 To Prevent Oil Ejecting from the HP-IP Turbine Bearings Chamber (Applicable to Rolls-Royce plc Models RB211 Trent 768-60, Trent 772-60, and Trent 772B-60 Turbofan Engines) |
| AD.06.05.11 |
Historical AD 2006-05-11 To Prevent Undetected Failure of the Shear Pin of Both PFS Units Simultaneously (Applicable to Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) Airplanes) (Revised by AD 2006-05-11 R1, effective March 27, 2006) |
| AD.06.04.01 |
AD 2006-04-01 To Prevent Injury to Crewmembers (Applicable to Airbus Model A300 B2 Series Airplanes; Model A300-B4 Series Airplanes; Model A300 B4-600 Series Airplanes; Model A300 B4-600R Series Airplanes; Model A300 F4 600R Series Airplanes; Model A300 C4-605R Variant F Airplanes; and Model A310-200 Series Airplanes; and Model A310-300 Series Airplanes) |
| AD.06.04.03 |
AD 2006-04-03 To Prevent Failure Of An Emergency Evacuation Slide Raft To Deploy And Inflate During An Emergency Situation (Applicable to Airbus Model A330-200 and -300 Series Airplanes, Model A340-200 and -300 Series Airplanes, and Model 340-541 and -642 Airplanes) |
| AD.06.04.04 |
AD 2006-04-04 To Identify And Provide Corrective Action For A Potentially Inoperative Smoke Detector (Applicable to Meggitt Model 602 Smoke Detectors Approved Under Technical Standard Order (TSO) TSO-C1C and Installed on Various Transport Category Airplanes) |
| AD.06.04.06 |
AD 2006-04-06 To Detect and Correct Wear of the Inboard Flap Trunnions (Applicable to Airbus Model A318-100 Series Airplanes, Model A319-100 Series Airplanes, Model A320-111 Airplanes, Model A320-200 Series Airplanes, and Model A321-100 Series Airplanes) |
| AD.06.04.07 |
AD 2006-04-07 To Prevent Pitch Oscillation (Vertical Bouncing) of the Fuselage (Applicable to BAE Systems (Operations) Limited Model BAe 146 and Avro 146-RJ Airplanes) |
| AD.06.04.08 |
AD 2006-04-08 To Prevent Uncommanded Movement of the Pilot's or Co-Pilot's Seat (Applicable to Airbus Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and Model C4-605R Variant F Airplanes (Collectively Called A300-600 Series Airplanes); and Model A310-300 Series Airplanes) |
| AD.06.04.09 |
AD 2006-04-09 To Prevent Camloc Fasteners from Disengaging and Interfering with an Inboard Rudder Pedal (Applicable to Bombardier Model CL-600-2C10 (Regional Jet Series 700, 701, & 702), CL-600-2D15 (Regional Jet Series 705), and CL-600-2D24 (Regional Jet Series 900) Airplanes) |
| AD.06.04.10 |
AD 2006-04-10 To Ensure that the Fire Extinguishing Bottles are Activated in the Event of an Engine or Auxiliary Power Unit (APU) Fire (Applicable to Cessna Model 500, 550, S550, 560, 560XL, and 750 Airplanes) |
| AD.06.03.10 |
AD 2006-03-10 To Prevent Contact Between The Horizontal Hinge Pin And The Adjacent Electrical Wire Harness (Applicable to Airbus Model A318-100 and A319-100 Series Airplanes; A320-111 Airplanes; A320-200 Series Airplanes; and A321-100 and A321-200 Series Airplanes) |
| AD.06.03.12 |
AD 2006-03-12 To Prevent Chafed Wire Bundles Near the Center Fuel Tank (Applicable to Boeing Model 737-100, -200, -200C, -300, -400, and -500 Series Airplanes) |
| AD.06.03.13 |
AD 2006-03-13 To Prevent Corrosion And Subsequent Cracking Of Studbolts (Applicable to McDonnell Douglas Model DC-10-10, DC-10-10F, DC-10-15, DC-10-30, DC-10-30F (KC-10A and KDC-10), DC-10-40, DC-10-40F, MD-10-10F, MD-10-30F, MD-11, and MD-11F Airplanes) |
| AD.06.02.12 |
AD 2006-02-12 To Prevent The Universal Bearing Of The Lower Rudder Mounting From Slipping Out Of The Bearing Support (Applicable to Glaser-Dirks Flugzeugbau GmbH Models DG-100 and DG-400 Sailplanes and DG Flugzeugbau GmbH Models DG-500 Elan Series and DG-500M Sailplanes) (See Correcting Federal Register 71 FR 7626, February 13, 2006) |
| AD.06.03.07 |
AD 2006-03-07 To Prevent Rapid Decompression Of The Airplane (Applicable to Fokker Model F.28 Mark 0070 and 0100 Airplanes) |
| AD.06.03.05 |
AD 2006-03-05 To Prevent Stress-corrosion Cracking (Applicable to Short Brothers Model SD3-60 SHERPA, SD3-SHERPA, and SD3-60 Airplanes) |
| AD.06.03.04 |
AD 2006-03-04 To Detect And Correct Fatigue Cracks In The Fuselage Skin (Applicable to McDonnell Douglas Model DC-8-33, DC-8-51, DC-8-53, DC-8-55, DC-8F-54, DC-8F-55, DC-8-63, DC-8-62F, DC-8-63F, DC-8-71, DC-8-73, DC-8-71F, DC-8-72F, and DC-8-73F Airplanes) |
| AD.06.03.06 |
AD 2006-03-06 To Prevent Uncommanded Movement Of The Pilot's or Copilot's Seat (Applicable to Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-135 Airplanes and Model EMB-145, -145ER, -145MR, -145LR, -145XR, -145MP, and -145EP Airplanes) |
| AD.06.03.09 |
AD 2006-03-09 To Prevent, in the Event of a Lightning Strike to the Horizontal Stabilizer (Applicable to Airbus Model A330-200 and -300 Series Airplanes, A340-200 and -300 Series Airplanes, and A340-541 and -642 Airplanes) (See Correcting Federal Register 71 FR 11462, March 7, 2006) |
| AD.06.04.13 |
Historical AD 2006-04-13 To Ensure that the Flightcrew is Advised of the Appropriate Procedures to Follow in the Event that the Cockpit Displays Go Blank or Malfunction (Applicable to Gulfstream Model GIV-X and GV-SP Series Airplanes) (Revised by AD 2006-04-13 R1, effective March 13, 2006) |
| AD.05.18.02 |
AD 2005-18-02 To Prevent Critical Life-limited Rotating Engine Part Failure (Applicable to Pratt and Whitney JT8D-209, -217, -217A, -217C, and -219 Turbofan Engines) (See Correcting Register 70 FR 71610, November 29, 2005) |
| AD.05.18.03 |
AD 2005-18-03 To Prevent Critical Life-Limited Rotating Engine Part Failure (Applicable to Pratt & Whitney PW2000 Series Turbofan Engines) |
| AD.06.02.08 |
Historical AD 2006-02-08 To Prevent Inflight Engine Shutdown (Applicable to Turbomeca Arriel 1B, 1D, 1D1, and 1S1 Turboshaft Engines) (Revised by AD 2006-02-08 R1, effective September 13, 2006) |
| AD.06.02.02 |
AD 2006-02-02 To Ensure that the APU Compartment is Isolated from the Rest of the Airplane (Applicable to Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-120, -120ER, -120FC, -120QC, and -120RT Airplanes) |
| AD.06.02.03 |
AD 2006-02-03 To Prevent A Short Circuit In The Fuse And Consequent Heat Damage (Applicable to Raytheon Model Hawker 800XP Airplanes) |
| AD.06.02.04 |
AD 2006-02-04 To Prevent Uncommanded Yaw Movements and Consequent Reduced Controllability of the Airplane (Applicable to Directives; Bombardier Model CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), and CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604) Airplanes) |
| AD.06.02.05 |
AD 2006-02-05 To Prevent Camloc Fasteners From Disengaging And Interfering With An Inboard Rudder Pedal (Applicable to Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) Airplanes) |
| AD.06.02.06 |
AD 2006-02-06 To Prevent Fatigue Cracking Of The Frame Foot Run-outs (Applicable to Airbus Model A310-203, -204, and -222 Airplanes, and Model A310-300 Series Airplanes) |
| AD.06.03.11 |
AD 2006-03-11 To Prevent Uncommanded Re-Engagement Of The Elevator Gust Lock (Applicable to British Aerospace Model HS 748 Airplanes) |
| AD.06.03.14 |
AD 2006-03-14 To Prevent Internal Oil Fires Caused by Coking and Carbon Buildup (Applicable to Rolls-Royce plc RB211 Trent 500 Series Turbofan Engines) |
| AD.06.01.02 |
AD 2006-01-02 To Prevent Fracture Of The Upper Lock Link Assembly Of The Nose Landing Gear (NLG) (Applicable to McDonnell Douglas Model DC-9-14, DC-9-15, and DC-9-15F Airplanes; Model DC-9-20, DC-9-30, DC-9-40, and DC-9-50 Series Airplanes; Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), and DC-9-87 (MD-87) Airplanes; Model MD-88 Airplanes; and Model MD-90-30 Airplanes) |
| AD.06.01.04 |
AD 2006-01-04 To Prevent Heat And Fire Damage To Equipment Adjacent To The Fan Venturi (Applicable to Raytheon Model DH.125, HS.125, and BH.125 Series Airplanes; Model BAe.125 Series 800A (C-29A and U-125), 800B, 1000A, and 1000B Airplanes; and Model Hawker 800 (including variant U-125A), and 1000 Airplanes) |
| AD.06.01.11 |
Historical AD 2006-01-11 To Provide A Safe Method To Detect Ice, Snow, Frost, Or Slush Adhering To The Upper Wing (A Critical Surface) Prior To Takeoff (Applicable to The Cessna Aircraft Company Models 208 and 208B Airplanes) (Revised by AD 2006-01-11 R1, effective February 22, 2006) |
| AD.06.01.01 |
AD 2006-01-01 To Find And Fix Discrepancies Of The Nose Wheel Steering Assembly (Applicable to Gulfstream Aerospace LP Model Gulfstream 100 Airplanes; and Model Astra SPX, and 1125 Westwind Astra Airplanes) |
| AD.06.01.05 |
AD 2006-01-05 To Prevent Failure Of Certain Components (Applicable to Honeywell International Inc. T5309, T5311, T5313B, T5317A, T5317A-1, and T5317B Series, and T53-L-9, T53-L-11, T53-L-13B, T53-L-13BA, T53-L-13B S/SA, T53-L-13B S/SB, T53-L-13B/D, and T53-L-703 Series Turboshaft Engines |
| AD.06.01.07 |
AD 2006-01-07 To Find and Fix Cracks in the Tension Ties (Applicable to Boeing Model 747-100, 747-100B, 747-200B, 747-200C, 747-200F, 747-400F, 747SR, and 747SP Series Airplanes) |
| AD.06.01.08 |
AD 2006-01-08 To Detect and Correct Cracking of the Fuselage Skin (Applicable to BAE Systems (Operations) Limited Model Avro 146-RJ Airplanes) |
| AD.06.01.09 |
AD 2006-01-09 To Ensure That Affected NLG Fitting Subassemblies Are Removed From Service (Applicable to BAE Systems (Operations) Limited Model BAe 146-100A and -200A Series Airplanes) |
| AD.06.01.10 |
AD 2006-01-10 To Prevent Inadvertent Trim Activation When the Autopilot is on and the Slats are Extended (Applicable to Airbus Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and Model C4-605R Variant F Airplanes (Collectively Called A300-600 Series Airplanes); and Airbus Model A310 Series Airplanes) |
| AD.06.03.02 |
AD 2006-03-02 To Prevent Chafing Between the Subject Oxygen Mask Box and the Adjacent Feeder Cables (Applicable to Dassault Model Falcon 2000 and Falcon 2000EX Airplanes) |
| AD.05.26.12 |
AD 2005-26-12 To Prevent Abnormal Or Uncontrolled Sailplane Release (Applicable to BURKHARDT GROB LUFT-UND RAUMFAHRT GmbH and CO KG Models G103 TWIN ASTIR, G103 TWIN II, G103A TWIN II ACRO, G103C TWIN III ACRO, and G 103 C Twin III SL Sailplanes) |
| AD.05.26.13 |
AD 2005-26-13 To Prevent Injection Wheel Cracks And Excessive Central Labyrinth Wear (Applicable to Turbomeca Artouste III Series Turboshaft Engines) |
| AD.05.26.15 |
AD 2005-26-15 To Prevent Discrepancies In The Elevator Control System (Applicable to Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-135 Airplanes; and Model EMB-145, -145ER, -145MR, -145LR, -145XR, -145MP, and -145EP Airplanes) |
| AD.05.26.16 |
AD 2005-26-16 To Detect And Correct Corrosion At The Lower Rim Area Of The Fuselage Rear Pressure Bulkhead (Applicable to Airbus Model A300 B2 and A300 B4 Series Airplanes; A300 B4-600, B4-600R, and F4-600R Series Airplanes, and C4-605R Variant F Airplanes (Collectively Called A300-600 Series Airplanes); and Airbus Model A310-200 and A310-300 Series Airplanes) |
| AD.05.26.17 |
AD 2005-26-17 To Detect And Correct Debonding Of The Skins On The Elevators (Applicable to Airbus Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and Model A300 C4-605R Variant F Airplanes (Collectively Called A300-600 Series Airplanes); and Model A310-200 and -300 Series Airplanes) |
| AD.05.26.18 |
AD 2005-26-18 To Prevent An Uncontained Failure Of The HPC Stage 11/12 Disc Spacer (Applicable to Rolls-Royce Deutschland (Formerly Rolls-Royce plc) Models Tay 650-15 and 651-54 Turbofan Engines) |
| AD.05.25.24 |
AD 2005-25-24 To Prevent Damage And Eventual Fracture Of The Yoke Assembly (Applicable to Boeing Model 777-200 and -300 Series Airplanes) |
| AD.05.26.04 |
AD 2005-26-04 To Prevent Migration of the Lower Gimbal Pin of the HSTA (Applicable to Bombardier Model CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), and CL-600-2B16 (CL-601-3A and CL-601-3R) Airplanes) |
| AD.05.25.27 |
AD 2005-25-27 To Prevent Structural Failure Of The Main Deck And Main Deck Cargo Door Areas (Applicable to Airbus Model A300 B2 Series Airplanes; A300 B4-103 and B4-203 Airplanes; and A310-203 Airplanes) |
| AD.05.25.07 |
AD 2005-25-07 To Prevent The Melting Or Burning Of The Plastic Cover Over The Air Conditioning Motor Module (Applicable to Raytheon Aircraft Company, Model 390, Premier 1 Airplanes) |
| AD.05.25.25 |
AD 2005-25-25 To Prevent Corrosion Of The Input Override Mechanism Bearings Of The Lateral Central Control Actuator (Applicable to Boeing Model 767-200, -300, and -300F Series Airplanes) |
| AD.05.25.26 |
AD 2005-25-26 To Detect And Correct Corrosion (Applicable to Boeing Model 747-400, 747-400D, and 747-400F Series Airplanes) |
| AD.05.25.16 |
AD 2005-25-16 To Detect and Correct Missing Attachment Rods (Applicable to Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model ERJ 170 Airplanes) |
| AD.05.25.17 |
AD 2005-25-17 To Prevent Fuel Accumulation and Subsequent Flammable Fuel Vapors in the APU Cowling (Applicable to Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-135BJ, -135ER, 135KE, -135KL, and -135LR Airplanes; and Model EMB-145, 145ER, -145MR, -145LR, -145XR, -145MP, and -145EP Airplanes) |
| AD.05.25.18 |
AD 2005-25-18 To Detect And Correct Cracking Or Other Discrepancies in the Upper And Lower Flanges Of The Front And Rear Spars Of The Wing (Applicable to Sabreliner Model NA-265, NA-265-20, NA-265-30, NA-265-40, NA-265-50, NA-265-60, NA-265-65, NA-265-70, and NA-265-80 Series Airplanes) |
| AD.05.25.19 |
AD 2005-25-19 To Prevent Failure Of The Stiffener Fittings (Applicable to Airbus Model A300 B2 Series Airplanes, Model A300 B4 Series Airplanes, Model A310-200 Series Airplanes, Model A310-300 Series Airplanes; and Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and Model C4-605R Variant F Airplanes (Collectively Called A300-600 Series Airplanes)) |
| AD.05.24.10 |
AD 2005-24-10 To Detect and Correct Incorrect Swaging Width of the Flight Control Cable Nicopress Seeves (Applicable to American Champion Aircraft Corporation Models 7AC, 7ACA, S7AC, 7BCM, 7CCM, S7CCM, 7DC, S7DC, 7EC, S7EC, 7ECA, 7FC, 7GC, 7GCA, 7GCAA, 7GCB, 7GCBA, 7GCBC, 7HC, 7JC, 7KC, 7KCAB, 8KCAB, and 8GCBC Airplanes) |
| AD.05.25.11 |
AD 2005-25-11 To Prevent Possible Multiple Uncontained LP Compressor Fan Blade Failure (Applicable to Rolls-Royce plc RB211 Trent 800 Series Turbofan Engines) |
| AD.05.25.14 |
AD 2005-25-14 To Prevent Total Electrical Failure (Applicable to BAE Systems (Operations) Limited (Jetstream) Model 4101 Airplanes) |
| AD.05.25.15 |
AD 2005-25-15 To Prevent Reduced Structural Integrity of the Engine Mount (Applicable to Dassault Model Falcon 2000 Airplanes Equipped With CFE Company CFE738-1-1B Turbofan Engines) |
| AD.05.26.07 |
AD 2005-26-07 To Ensure That The Flightcrew Is Advised Of Appropriate Procedures To Follow In The Event Of A Fuel Leak (Applicable to Airbus Model A318-100, A319-100, A320-200, A321-100, and A321-200 Series Airplanes; and Model A320-111 Airplanes) |
| AD.05.24.11 |
AD 2005-24-11 To Prevent The Unscrewing Of The Spring Cartridge Clevis From Jamming The Elevator (Applicable to Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-135 Airplanes and Model EMB-145, -145ER, -145MR, -145LR, -145XR, -145MP, and -145EP Airplanes) (See Correcting Federal Registers 71 FR 231 January 4, 2006, and 71 FR 52415, September 6, 2006) |
| AD.05.24.12 |
AD 2005-24-12 To Prevent Asymmetric Reverse Thrust And Consequent Loss Of Control Of The Airplane During Reverse Thrust Operation (Applicable to Bombardier Model CL-600-2C10 (Regional Jet Series 700, 701, and 702) Airplanes) |
| AD.05.25.01 |
AD 2005-25-01 To Prevent Chafed Electrical Harnesses (Applicable to Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-120, -120ER, -120FC, -120QC, and -120RT Airplanes) (See Correcting Federal Register 71 FR 231A, January 4, 2006) |
| AD.05.24.07 |
AD 2005-24-07 To Prevent Structural Failure Of The Outer Panel And Spar (Applicable to Pacific Aerospace Corporation Ltd. Model 750XL Airplanes) |
| AD.05.25.20 |
AD 2005-25-20 To Prevent Cracking Of The Fuselage Skin In The Area Of The VHF2 antenna (Applicable to Airbus Model A330-300, A340-200, and A340-300 Series Airplanes) |
| AD.05.24.02 |
AD 2005-24-02 To Prevent Flame Backflow Into The APU Compartment Through The Eductor (Applicable to Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-135 Airplanes and Model EMB-145, -145ER, -145MR, -145LR, -145XR, -145MP, and -145EP Airplanes) |
| AD.05.24.03 |
AD 2005-24-03 To Prevent Inadequate Fastener Clamp-up (Applicable to Boeing Model 737-600, -700, -700C, and -800 Series Airplanes) |
| AD.05.24.04 |
AD 2005-24-04 To Prevent Overheating of the Output Wiring of the Frequency Converters (Applicable to Boeing Model 767-300 Series Airplanes) |
| AD.05.25.12 |
AD 2005-25-12 To Prevent Failure Of 2nd Stage Axial Compressor Wheel Blades (Applicable to Turbomeca Astazou XIV B and XIV H Turboshaft Engines) |
| AD.05.23.12 |
AD 2005-23-12 To Ensure That Fatigue Cracking Of Certain Structural Elements Is Detected And Corrected (Applicable to BAE Systems (Operations) Limited Model BAe 146 and Model Avro 146-RJ Airplanes) |
| AD.05.23.19 |
AD 2005-23-19 To Prevent The Outboard Overhead Stowage Bins Opening During Flight And Releasing Baggage (Applicable to Boeing Model 767-200 and -300 Series Airplanes) |
| AD.05.23.20 |
AD 2005-23-20 To Ensure that the APU Compartment is Isolated from the Rest of the Airplane (Applicable to Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-135 Airplanes, and Model EMB-145, -145ER, -145MR, -145LR, -145XR, -145MP, and -145EP Airplanes) |
| AD.05.25.06 |
AD 2005-25-06 To Prevent Binding Of The Flight Controls Caused By Loose Attachment Screws (Applicable to Fokker Model F27 Mark 050 Airplanes) |
| AD.05.25.04 |
AD 2005-25-04 To Prevent Failure of Multiple Hinge Fittings (Applicable to Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-135BJ, -135ER, -135KE, -135KL, -135LR, -145, -145ER, -145MR, -145LR,-145XR, -145MP, and -145EP Airplanes |
| AD.05.23.15 |
AD 2005-23-15 To Ensure That The Flightcrew And Maintenance Personnel Are Advised Of Procedures (Applicable to British Aerospace Model BAC 1-11 200 and 400 Series Airplanes) |
| AD.05.23.16 |
AD 2005-23-16 To Prevent Chafed Wire Bundles Near The Center Fuel Tank (Applicable to Boeing Model 737-600, -700, -700C, -800, and -900 Series Airplanes) |
| AD.05.23.17 |
AD 2005-23-17 To Detect And Correct Chafing Of The Wiring Behind The P15 Refuel Panel (Applicable to Boeing Model 737 Airplanes) |
| AD.05.22.13 |
AD 2005-22-13 To Detect And Correct Any Part Number (P/N) 532.10.12.077 or FAA-approved Equivalent Part Number Bolts That Do Not Have White Primed And Painted Heads (Applicable To Pilatus Aircraft Ltd. Models PC-12 and PC-12/45 Airplanes) |
| AD.05.22.14 |
AD 2005-22-14 To Detect, Correct, And Prevent Chafing Of The Cables (Applicable To GROB-WERKE Model G120A Airplanes) |
| AD.05.23.02 |
AD 2005-23-02 To Prevent Air Leakage Around the Seal of the Outer Manhole Covers of the ACTs, (Applicable to Airbus Model A319-100 Series Airplanes, Model A320-111 Airplanes, Model A320-200 Series Airplanes, and Model A321-100 Series Airplanes) |
| AD.05.23.03 |
AD 2005-23-03 To Prevent Failure of the Spherical Accumulator for the Main Hydraulic System (Applicable to Learjet Model 23, 24, 24A, 24B, 24B-A, 24C, 24D, 24D-A, 24E, 24F, 24F-A, 25, 25A, 25B, 25C, 25D, and 25F Airplanes) |
| AD.05.23.04 |
AD 2005-23-04 To Prevent Uncommanded Feathering Of The Propeller (Applicable to Saab Model SAAB 2000 Airplanes) |
| AD.05.23.05 |
AD 2005-23-05 To Prevent Failure Of The Escape Slide/Raft To Deploy Correctly (Applicable to Airbus Model A319-100, A320-200, and A321-100 and -200 Series Airplanes) |
| AD.05.23.06 |
AD 2005-23-06 To Prevent Failure Of The Thrust Reverser Accumulators (Applicable to Learjet Model 23, 24, 24A, 24B, 24B-A, 24D, 24D-A, 24E, 24F, 25, 25A, 25B, 25C, 25D, and 25F Airplanes Modified by Supplemental Type Certificate SA1731SW, SA1669SW, or SA1670SW) |
| AD.05.23.08 |
AD 2005-23-08 To Prevent Fatigue Cracking Of The Forward Fitting Of Fuselage Frame FR47 (Applicable to Airbus Model A300 B4-600 and A300 B4-600R Series Airplanes; and A300 F4-605R and A300 C4-605R Variant F Airplanes) |
| AD.05.24.08 |
AD 2005-24-08 To Prevent Cracked Propeller Hubs (Applicable to McCauley Propeller Systems Five-Blade Propeller Assemblies) |
| AD.05.22.11 |
AD 2005-22-11 To Detect And Correct Fatigue Cracking Of The Propeller Hub (Applicable To Mitsubishi Model YS-11 Airplanes, and Model YS-11A-200, YS-11A-300, YS-11A-500, and YS-11A-600 Series Airplanes) |
| AD.05.23.21 |
AD 2005-23-21 To Detect And Correct Fatigue Cracking Of The Junction Between The Thrust Reverser Forward Frame And The 12 O'Clock Beam (Applicable to Airbus Model A340-200 and A340-300 Series Airplanes) |
| AD.03.19.14 |
AD 2003-19-14 R2 To Prevent Damage To The Fuselage During Limit Load Flight (Applicable To BURKHART GROB LUFT--UND RAUMFAHRT GmbH and CO KG Models G103 TWIN ASTIR, G103A TWIN II ACRO, and G103C TWIN III ACRO Sailplanes) |
| AD.05.22.05 |
AD 2005-22-05 To Prevent Chafing Of The Fuel Pump Cables (Applicable To Airbus Model A320-111, -211, -212, And -231 Airplanes) |
| AD.05.22.06 |
AD 2005-22-06 To Detect And Correct Cracks In The Frame Web (Applicable To Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747SR, And 747SP Series Airplanes) |
| AD.05.22.07 |
AD 2005-22-07 To Detect And Correct A Damaged Electrical Bonding Surface Of The APU Battery And APU Start Transformer Rectifier Unit (TRU) Ground Connections (Applicable To Boeing Model 757-200, -200PF, And -300 Series Airplanes) |
| AD.05.22.08 |
AD 2005-22-08 To Prevent Failure Of The TAT Sensor (Applicable To Empresa Brasileira De Aeronautica S.A. (EMBRAER) Model EMB-135BJ, -135ER, -135KE, -135KL, -135LR, -145, -145ER, -145MR, -145LR, -145XR, -145MP, And -145EP Airplanes) |
| AD.05.22.03 |
AD 2005-22-03 To Prevent Uncontained Turbine Wheel Failure (Applicable To Rolls-Royce Corporation (Formerly Allison Engine Company) 501-D22A, 501-D22C, And 501-D22G Turboprop Engines) |
| AD.05.23.01 |
AD 2005-23-01 To Detect And Correct Cracking In The Aft Pressure Bulkhead (Applicable to Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) Airplanes) |
| AD.05.23.10 |
AD 2005-23-10 To Ensure Proper Functioning Of The Elevator Servo Controls (Applicable to Airbus Model A330-200 and A330-300 Series Airplanes; and Model A340-200 and A340-300 Series Airplanes) |
| AD.05.21.05 |
AD 2005-21-05 To Detect And Prevent Cracks In The Fan Disc (Applicable To Rolls-Royce Deutschland Ltd & Co KG (Formerly Rolls-Royce AD 2005-21-05 Deutschland Gmbh, Formerly BMW Rolls-Royce Gmbh) Models BR700-710A1-10 And BR700-710A2-20 Turbofan Engines) |
| AD.05.21.06 |
AD 2005-21-06 To Detect And Correct Such Fatigue Cracks (Applicable To Boeing Model 737-600, -700, -700C, - 800, And -900 Series Airplanes) |
| AD.05.21.01 |
AD 2005-21-01 To Prevent Oil Fires; Fracture Of The HPT Shaft Which Can Result In Uncontained Release Of Engine Fragments; Engine Fire; In-Flight Engine Shutdown; And Possible Airplane Damage (Applicable To Pratt & Whitney JT8D-200 Series Turbofan Engines) |
| AD.05.21.03 |
AD 2005-21-03 To Prevent Loss Of A Blade, Loss Of Tail Rotor Control, And Subsequent Loss Of Control Of The Helicopter (Applicable To Bell Helicopter Textron Canada Model 206A, A-1, B, B-1, L, L-1, L-3, L-4 Helicopters) |
| AD.05.20.39 |
AD 2005-20-39 To Prevent Collapse Of The Mlg, Or Damage To Hydraulic Tubing Or The Aileron Control Cables (Applicable to Boeing Model 737-100, -200, -200C, -300, -400, and -500 Series Airplanes) |
| AD.05.20.40 |
AD 2005-20-40 To Prevent An Undetected Flap Skew (Applicable To Boeing Model 757-200, -200CB, and -200PF Series Airplanes) |
| AD.05.20.41 |
AD 2005-20-41 Reports Of Damage And Subsequent Failure Of The Support Brackets And Associated Fasteners For The Hydraulic Lines (Applicable To Boeing Model 757-200, -200PF, and -300 Series Airplanes, Powered by Pratt and Whitney PW2000 Series Engines) |
| AD.05.20.26 |
AD 2005-20-26 To Prevent Series 312 Box Mounted Seats From Detaching From The Passenger Compartment Floor (Applicable to Aviointeriors S.p.A. (formerly ALVEN), Series 312 Box Mounted Seats) (See Correcting Federal Register 70 FR 75004, December 19, 2005) |
| AD.05.20.28 |
AD 2005-20-28 To Prevent Inadequate Lighting and Marking of the Escape Path (Applicable to Airbus Model A319-100 Series Airplanes; Model A320-111 Airplanes; Model A320-200 Series Airplanes, and Model A321-100 and -200 Series Airplanes) |
| AD.05.20.29 |
AD 2005-20-29 To Detect And Correct Cracking In The Upper Chords Of The Upper Deck Floor Beams (Applicable To Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-300, 747SP, and 747SR Series Airplanes) |
| AD.05.20.30 |
AD 2005-20-30 To Prevent The Loss Of The Structural Integrity Of The Fuselage (Applicable To Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-300, 747SP, and 747SR Series Airplanes) |
| AD.05.20.32 |
AD 2005-20-32 To Prevent Disbonding Of The Elevator Assembly (Applicable to Airbus Model A330-200 and -300 and A340-200 and -300 Series Airplanes) |
| AD.05.20.33 |
AD 2005-20-33 To Detect And Correct Fatigue Cracking Of The Forward And Aft Edge Frames Of The Lower Lobe Forward Cargo Door (FCD) Cutout (Applicable to Boeing Model 727, 727C, 727-100, and 727-100C Series Airplanes) |
| AD.05.20.36 |
AD 2005-20-36 To Prevent an Ignition Source For Fuel Vapor in the Wing (Applicable to Airbus Model A320-111 Airplanes; and Model A320-200, A321-100, and A321-200 Series Airplanes) |
| AD.05.18.22 |
AD 2005-18-22 To Detect And Correct Chafing Conditions In The Engine Installation (Applicable To Raytheon Aircraft Company Model 390 Premier 1 Airplanes) |
| AD.05.20.14 |
AD 2005-20-14 To Prevent An Ignition Source In The ACT (Applicable To Airbus Model A300 B4-620, A310-304, A310-324, and A310-325 Airplanes) |
| AD.05.20.15 |
AD 2005-20-15 To Prevent Failure Of A Rudder Pedal Torque Tube (Applicable To McDonnell Douglas Model DC-10-10 and DC-10-10F Airplanes; Model DC-10-15 Airplanes; Model DC-10-30 and DC-10-30F (KC-10A and KDC-10) Airplanes; Model DC-10-40 and DC-10-40F Airplanes; Model MD-10-10F and MD-10-30F Airplanes; and Model MD-11 and MD-11F Airplanes) |
| AD.05.20.13 |
AD 2005-20-13 To Detect And Correct Cracks In The Frames (Applicable To Boeing Model 727 Airplanes) |
| AD.05.20.16 |
AD 2005-20-16 To Prevent A Lifted Slat (Applicable To Boeing Model 737-100, -200, And -200C Series Airplanes) |
| AD.05.20.17 |
AD 2005-20-17 To Ensure Normal Braking Is Available (Applicable To Airbus Model A319-100 Series Airplanes; Model A320-111 Series Airplanes; Model A320-200 Series Airplanes; And Model A321-100 And -200 Series Airplanes) |
| AD.05.20.24 |
AD 2005-20-24 To Detect And Correct Cracks In The Fuselage Skin (Applicable to SOCATA--Groupe AEROSPATIALE Model TBM 700 Airplanes) |
| AD.05.20.18 |
AD 2005-20-18 To Prevent Cracking and Other Damage of the Actuator Attach Fittings of the Trailing Edge Flaps (Applicable to Boeing Model 747-100, -200B, -200F, -200C, -100B, -300, -100B SUD, -400, -400D, and -400F Series Airplanes; and Model 747SR Series Airplanes) |